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EP2396526B1 - Aircraft engine with cooling for an electric starting device - Google Patents

Aircraft engine with cooling for an electric starting device Download PDF

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Publication number
EP2396526B1
EP2396526B1 EP10706305A EP10706305A EP2396526B1 EP 2396526 B1 EP2396526 B1 EP 2396526B1 EP 10706305 A EP10706305 A EP 10706305A EP 10706305 A EP10706305 A EP 10706305A EP 2396526 B1 EP2396526 B1 EP 2396526B1
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EP
European Patent Office
Prior art keywords
pump
fuel
electric
high pressure
pressure pump
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP10706305A
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German (de)
French (fr)
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EP2396526A1 (en
Inventor
Christian Aurousseau
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Publication date
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Publication of EP2396526A1 publication Critical patent/EP2396526A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/236—Fuel delivery systems comprising two or more pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to the cooling of electric starting devices for aeronautical engines.
  • a particular field of application of the invention is that of aeronautical gas turbine engines, in particular turbo-reactors.
  • the starting of an aeronautical engine is conventionally provided by an electric machine driving an engine shaft.
  • the electrical machine may be an electric motor or a machine forming a starter / generator or S / G ("Starter / Generator") operating in motor mode at startup and synchronous generator mode thereafter.
  • the fuel is conventionally used as a cooling fluid, either directly or by heat exchange with a coolant, for example oil.
  • the fuel is pumped into a tank and fed to an engine fuel system that includes a high pressure pump.
  • This delivers fuel under high pressure to a main supply circuit of the combustion chamber of the engine.
  • the high pressure pump is typically a gear pump driven from a motor shaft via a mechanical transmission gearbox or Accessory Gear Box (AGB).
  • the object of the invention is to propose a solution to the cooling problem of the electric starting device which does not have such disadvantages.
  • an aeronautical engine comprising a fuel pumping device comprising a high pressure pump having an inlet connected to a low pressure fuel line and an output connected to a main high pressure fuel supply circuit, a device electric starter motor and a cooling device of the electric start device connected to the pumping device for cooling by fuel circulation, wherein the cooling device is supplied with fuel by a pump driven by an electric motor independently of the high pressure pump and having an input connected to the pumping device, upstream of the high-pressure pump.
  • the pumping device comprises a low pressure pump driven from a motor shaft and having an output connected to the input of the high pressure pump, and the electric pump supplying the cooling device has its input connected to the device. pumping between the output of the low pressure pump and the inlet of the high pressure pump.
  • the electric pump can be turned off, the low pressure pump then being driven at a speed sufficient to supply the cooling device effectively, the cooling may be required permanently when the Electric start device is type S / G.
  • the electric pump supplying the cooling device has an output connected to the main circuit for supplying high pressure fuel.
  • the electric pump can contribute to providing sufficient fuel flow to the main fuel supply circuit. It is then possible to use a high-pressure pump of the gear type, but with a smaller displacement, or a centrifugal-type high-pressure pump, which has a lower mass and greater reliability than a gear pump, although it delivers lower fuel flow at low starting speed.
  • the cooling device comprises a first coolant circulation circuit connected to the electrical starting device, a second fuel circulation circuit connected to the electric pump supplying the cooling device and a heat exchanger crossed. by the first circuit and the second circuit.
  • the cooling device may be arranged to cool an electric starter of the electric starter device and an electronic control circuit of power of the electric starter.
  • gas turbine engine engines such as that shown very schematically on the figure 1 the invention is however applicable to other aircraft engines, including helicopter turbines, as well as to land and naval engines.
  • the engine of the figure 1 comprises a combustion chamber 1, the combustion gases resulting therefrom driving a high-pressure turbine 2 and a low-pressure turbine 3.
  • the turbine 2 is coupled by a shaft to a high-pressure compressor supplying the combustion chamber with compressed air. pressure while the low pressure turbine is coupled by another shaft to a blower 5 at the engine inlet.
  • An AGB 7 transmission box or accessory relay box is connected by a mechanical power plug 9 to a turbine shaft and includes a set of pinions for mechanical coupling with a number of accessories.
  • the figure 2 is a simplified diagram showing in particular a motor part according to one embodiment of the invention.
  • Reference numeral 10 denotes an aircraft fuel tank with a fuel pump 12 driven by an electric motor 14 and supplying a line 16 which conveys fuel to the engine 20.
  • LPSOV Low Pressure Shutoff
  • the engine 20 includes a pumping device 22 supplying fuel to a main fuel supply circuit of the engine combustion chamber with high pressure fuel.
  • the pumping device 22 comprises a low-pressure fuel pump 24 whose inlet is connected to the pipe 16 and whose outlet is connected to the inlet of a high-pressure fuel pump 26 via a pipe 28.
  • the output of the high pressure pump 26 is connected to a line 30 of the main supply circuit.
  • a metering device 32 receives the fuel flow supplied by the high pressure pump to supply the combustion chamber (not shown) of the engine with a regulated high pressure fuel flow rate.
  • the low pressure pump 24 is for example a centrifugal pump driven mechanically via the AGB.
  • the high pressure pump 26 is here a gear pump also driven mechanically via the AGB.
  • the motor 20 comprises an electric starting device 40, for example of the S / G type.
  • the device 40 is housed in a housing 42. It comprises an electric machine 44 having a shaft 46 which protrudes out of the housing 42 for mechanical coupling with the AGB. In start-up mode, the electric machine operates in motor mode to drive a turbine shaft through the AGB while after starting, when the turbine shaft has reached a sufficient speed, the operation of the electric machine is switched to generator mode.
  • a housing 48 encloses the power electronics for the control of the electrical machine 44. The housing is electrically connected to an electronic engine control circuit (not shown). The housing 48 may be attached to the housing 42 as illustrated, or be independent therefrom.
  • the cooling of the electric starting device 40 is provided by fuel taken from the pumping device by a pump 50 driven by an electric motor 52 itself controlled by the electronic engine control circuit, the driving the pump 50 thus being independent of that of the high pressure pump 26.
  • the cooling is ensured by heat exchange with a coolant collecting calories in the starting device 40.
  • Heat transfer fluid circulation channels 42a are formed in the walls of the casing 42 and close to the casing 48.
  • the fluid coolant is for example oil also used for lubrication of various organs including AGB.
  • the oil circuit with an oil pump (not shown) comprises a conduit 54 which leads the oil to the channels 42a and a conduit 56 which recovers the oil having circulated in the channels 42 a and, where appropriate, also having used for bearing lubrication bearing shaft 46 in housing 42.
  • the heat exchange between the fuel and the oil is carried out within an exchanger 58.
  • the exchanger 58 comprises an internal oil circuit which receives the oil from the starting device 40 via the pipe 56 and which restores the oil cooled to the oil circuit, and an internal fuel circuit forming part of a fuel circuit 60 which has an input connected to the output of the pump 50 and an output connected to the tank 10.
  • the inlet of the pump 50 is connected to the pipe 28, that is to say between the output of the low pressure pump 24 and the inlet of the high pressure pump 26.
  • the electric pump 50 can be stopped, the speed of the turbine shaft driving the low pressure pump 24 becoming sufficient to provide the cooling fuel flow rate required to effectively cool the starting device after switching the machine 44 into operation. generator.
  • the stopping of the pump 50 is controlled by deactivation of the electric motor 52 under the control of the electronic engine control unit when the speed of the turbine shaft exceeds a given minimum value.
  • the electric pump 50 is connected to the pipe supplying the high pressure pump.
  • the output of the electric pump 50 can also be connected via a line 62 to the pipe 30 of the main circuit for supplying pressurized fuel, upstream of the metering device 32.
  • the pump 50 can contribute to the provision of sufficient fuel flow to the combustion chamber. This requirement to provide sufficient fuel flow during startup no longer weighs on the high pressure pump 26, we can then advantageously use for it a centrifugal pump rather than a positive displacement gear pump.
  • a nonreturn valve 64 is mounted on the pipe 62 to prevent, after starting, fuel from the high pressure pump 26 circulating in the pipe 62.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Motor Or Generator Cooling System (AREA)
  • Supercharger (AREA)
  • Fuel-Injection Apparatus (AREA)

Description

Arrière-plan de l'inventionBackground of the invention

L'invention concerne le refroidissement de dispositifs électriques de démarrage de moteurs aéronautiques.The invention relates to the cooling of electric starting devices for aeronautical engines.

Un domaine particulier d'application de l'invention est celui des moteurs aéronautiques à turbine à gaz, notamment les turbo-réacteurs.A particular field of application of the invention is that of aeronautical gas turbine engines, in particular turbo-reactors.

Le démarrage de moteur aéronautique est classiquement assuré par une machine électrique entraînant un arbre du moteur. La machine électrique peut être un moteur électrique ou une machine formant démarreur/générateur ou S/G ("Starter/Generator") fonctionnant en mode moteur au démarrage et en mode génératrice synchrone ensuite.The starting of an aeronautical engine is conventionally provided by an electric machine driving an engine shaft. The electrical machine may be an electric motor or a machine forming a starter / generator or S / G ("Starter / Generator") operating in motor mode at startup and synchronous generator mode thereafter.

Il est nécessaire, au démarrage, d'évacuer les calories produites par le dispositif électrique de démarrage, à savoir par la machine électrique elle-même et de préférence aussi par le circuit électronique de puissance utilisé pour commander la machine électrique, comme indiqué par exemple dans le document EP 1 953 899 .It is necessary, at startup, to evacuate the calories produced by the electrical starting device, namely by the electric machine itself and preferably also by the electronic power circuit used to control the electric machine, as indicated for example in the document EP 1,953,899 .

Dans un moteur aéronautique, le carburant est classiquement utilisé comme fluide de refroidissement, soit directement, soit par échange thermique avec un fluide caloporteur, par exemple de l'huile.In an aeronautical engine, the fuel is conventionally used as a cooling fluid, either directly or by heat exchange with a coolant, for example oil.

Le carburant est pompé dans un réservoir et amené à un circuit de carburant du moteur qui comprend une pompe haute pression. Celle-ci délivre du carburant sous haute pression à un circuit principal d'alimentation de la chambre de combustion du moteur. La pompe haute pression est typiquement une pompe à engrenages entraînée à partir d'un arbre du moteur par l'intermédiaire d'une boîte mécanique de transmission ou boîte de relais d'accessoires, ou AGB ("Accessory Gear Box").The fuel is pumped into a tank and fed to an engine fuel system that includes a high pressure pump. This delivers fuel under high pressure to a main supply circuit of the combustion chamber of the engine. The high pressure pump is typically a gear pump driven from a motor shaft via a mechanical transmission gearbox or Accessory Gear Box (AGB).

Il a été proposé d'assurer le refroidissement d'un dispositif électrique de démarrage par du carburant prélevé en sortie de la pompe haute pression du circuit de pompage du moteur. Pour assurer un débit suffisant de carburant de refroidissement au bas régime de démarrage, il est nécessaire de conférer à la pompe haute pression une cylindrée importante. Une telle cylindrée est alors largement surdimensionnée pour fournir le débit requis par le circuit d'alimentation principal lors du fonctionnement du moteur en régime nominal, ce qui impose de dériver une part importante du carburant fourni par la pompe haute pression afin de le retourner vers la basse pression. L'utilisation de pompes supplémentaires entraînées mécaniquement par le moteur pour alimenter le dispositif de refroidissement du dispositif électrique de démarrage pourrait être envisagée. Mais une telle solution se traduit par un accroissement de masse, par la nécessité d'une liaison mécanique supplémentaire avec l'AGB et pose problème à fort régime en dérivant un débit de carburant alors trop important.It has been proposed to provide the cooling of an electrical starting device with fuel taken from the outlet of the high pressure pump of the engine pumping circuit. To ensure a sufficient flow of cooling fuel at low starting speed, it is necessary to give the high pressure pump a large displacement. Such a displacement is then largely oversized to provide the flow required by the main supply circuit during the operating the engine at rated speed, which requires to divert a large part of the fuel supplied by the high pressure pump to return it to the low pressure. The use of additional pumps mechanically driven by the engine to power the cooling device of the electric start device could be considered. But such a solution results in an increase in mass, the need for an additional mechanical connection with the AGB and is problematic at high speed by deriving a fuel flow then too important.

Il a été proposé dans le document US 3 733 816 de refroidir un calculateur électronique d'un moteur à turbine à gaz au moyen de carburant fourni par une pompe située en amont de la pompe de carburant haute pression, en série avec cette dernière, les deux pompes étant montées sur une arbre d'entraînement commun couplé au moteur.It was proposed in the document US 3,733,816 to cool an electronic computer of a gas turbine engine by means of fuel supplied by a pump located upstream of the high pressure fuel pump, in series with the latter, the two pumps being mounted on a common drive shaft coupled to the engine.

Objet et résumé de l'inventionObject and summary of the invention

L'invention a pour but de proposer une solution au problème de refroidissement du dispositif électrique de démarrage ne présentant pas de tels inconvénients.The object of the invention is to propose a solution to the cooling problem of the electric starting device which does not have such disadvantages.

Ce but est atteint grâce à un moteur aéronautique comprenant un dispositif de pompage de carburant comportant une pompe haute pression ayant une entrée reliée à une conduite de carburant basse pression et une sortie reliée à un circuit principal d'alimentation en carburant haute pression, un dispositif électrique de démarrage du moteur et un dispositif de refroidissement du dispositif électrique de démarrage relié au dispositif de pompage pour assurer le refroidissement par circulation de carburant, moteur dans lequel le dispositif de refroidissement est alimenté en carburant par une pompe entraînée par un moteur électrique indépendamment de la pompe haute pression et ayant une entrée reliée au dispositif de pompage, en amont de la pompe haute-pression.This object is achieved by an aeronautical engine comprising a fuel pumping device comprising a high pressure pump having an inlet connected to a low pressure fuel line and an output connected to a main high pressure fuel supply circuit, a device electric starter motor and a cooling device of the electric start device connected to the pumping device for cooling by fuel circulation, wherein the cooling device is supplied with fuel by a pump driven by an electric motor independently of the high pressure pump and having an input connected to the pumping device, upstream of the high-pressure pump.

L'utilisation d'une telle pompe électrique permet d'assurer un débit suffisant de carburant de refroidissement à bas régime sans surdimensionnement de la cylindrée de la pompe haute pression et se traduit par un encombrement moindre et une mise en oeuvre moins complexe que l'ajout d'une pompe entraînée mécaniquement par le moteur.The use of such an electric pump ensures a sufficient flow of cooling fuel at low speed without oversizing the displacement of the high pressure pump and results in a smaller footprint and a less complex implementation that the addition of a pump driven mechanically by the engine.

Avantageusement, le dispositif de pompage comprend une pompe basse pression entraînée à partir d'un arbre du moteur et ayant une sortie reliée à l'entrée de la pompe haute pression, et la pompe électrique alimentant le dispositif de refroidissement a son entrée reliée au dispositif de pompage entre la sortie de la pompe basse pression et l'entrée de la pompe haute pression.Advantageously, the pumping device comprises a low pressure pump driven from a motor shaft and having an output connected to the input of the high pressure pump, and the electric pump supplying the cooling device has its input connected to the device. pumping between the output of the low pressure pump and the inlet of the high pressure pump.

Ainsi, après démarrage, lorsque le régime du moteur augmente, la pompe électrique peut être désactivée, la pompe basse pression étant alors entraînée à une vitesse suffisante pour alimenter le dispositif de refroidissement de façon efficace, le refroidissement pouvant être requis de façon permanente lorsque le dispositif électrique de démarrage est de type S/G.Thus, after starting, when the engine speed increases, the electric pump can be turned off, the low pressure pump then being driven at a speed sufficient to supply the cooling device effectively, the cooling may be required permanently when the Electric start device is type S / G.

Avantageusement encore, la pompe électrique alimentant le dispositif de refroidissement a une sortie reliée au circuit principal d'alimentation en carburant haute pression.Advantageously, the electric pump supplying the cooling device has an output connected to the main circuit for supplying high pressure fuel.

Ainsi, lors de la phase de démarrage, la pompe électrique peut contribuer à fournir un débit de carburant suffisant au circuit principal d'alimentation en carburant. On peut alors utiliser une pompe haute pression du type à engrenages, mais avec une cylindrée plus faible, ou une pompe haute pression de type centrifuge, qui a une moindre masse et une meilleure fiabilité qu'une pompe à engrenages, bien qu'elle délivre un plus faible débit de carburant au bas régime de démarrage.Thus, during the start-up phase, the electric pump can contribute to providing sufficient fuel flow to the main fuel supply circuit. It is then possible to use a high-pressure pump of the gear type, but with a smaller displacement, or a centrifugal-type high-pressure pump, which has a lower mass and greater reliability than a gear pump, although it delivers lower fuel flow at low starting speed.

Selon un mode particulier de réalisation, le dispositif de refroidissement comprend un premier circuit de circulation de fluide caloporteur relié au dispositif électrique de démarrage, un deuxième circuit de circulation de carburant relié à la pompe électrique alimentant le dispositif de refroidissement et un échangeur de chaleur traversé par le premier circuit et le deuxième circuit.According to a particular embodiment, the cooling device comprises a first coolant circulation circuit connected to the electrical starting device, a second fuel circulation circuit connected to the electric pump supplying the cooling device and a heat exchanger crossed. by the first circuit and the second circuit.

Le dispositif de refroidissement peut être agencé pour refroidir un démarreur électrique du dispositif électrique de démarrage et un circuit électronique de commande de puissance du démarreur électrique.The cooling device may be arranged to cool an electric starter of the electric starter device and an electronic control circuit of power of the electric starter.

Brève description des dessinsBrief description of the drawings

L'invention sera mieux comprise à la lecture de la description faite ci-après, à titre indicatif mais non limitatif, en référence au dessin annexé sur lequel

  • la figure 1 illustre très schématiquement un moteur aéronautique à turbine à gaz ; et
  • la figure 2 illustre un mode de réalisation de l'invention.
The invention will be better understood on reading the description given below, by way of indication but without limitation, with reference to the accompanying drawing in which:
  • the figure 1 illustrates very schematically a gas turbine engine; and
  • the figure 2 illustrates an embodiment of the invention.

Description détaillée de modes de réalisationDetailed description of embodiments

Un domaine d'application de l'invention est celui des moteurs d'avions à turbine à gaz, tel que celui représenté très schématiquement sur la figure 1, l'invention étant toutefois applicable à d'autres moteurs aéronautiques, notamment des turbines d'hélicoptères, ainsi qu'à des moteurs terrestres et navals.One field of application of the invention is that of gas turbine engine engines, such as that shown very schematically on the figure 1 the invention is however applicable to other aircraft engines, including helicopter turbines, as well as to land and naval engines.

Le moteur de la figure 1 comprend une chambre de combustion 1, les gaz de combustion issus de celle-ci entraînant une turbine haute pression 2 et une turbine basse pression 3. La turbine 2 est couplée par un arbre à un compresseur haute pression alimentant la chambre de combustion en air sous pression tandis que la turbine basse pression est couplée par un autre arbre à une soufflante 5 en entrée du moteur.The engine of the figure 1 comprises a combustion chamber 1, the combustion gases resulting therefrom driving a high-pressure turbine 2 and a low-pressure turbine 3. The turbine 2 is coupled by a shaft to a high-pressure compressor supplying the combustion chamber with compressed air. pressure while the low pressure turbine is coupled by another shaft to a blower 5 at the engine inlet.

Une boîte de transmission ou boîte de relais d'accessoires AGB 7 est reliée par une prise de puissance mécanique 9 à un arbre de turbine et comprend un ensemble de pignons pour couplage mécanique avec un certain nombre d'accessoires.An AGB 7 transmission box or accessory relay box is connected by a mechanical power plug 9 to a turbine shaft and includes a set of pinions for mechanical coupling with a number of accessories.

La figure 2 est un schéma simplifié montrant notamment une partie de moteur selon un mode de réalisation de l'invention.The figure 2 is a simplified diagram showing in particular a motor part according to one embodiment of the invention.

La référence 10 désigne un réservoir de carburant avion avec une pompe de carburant 12 entraînée par un moteur électrique 14 et alimentant une conduite 16 qui achemine du carburant au moteur 20. Une vanne de coupure basse-pression 18 ou LPSOV ("Low Pressure Shut-Off Valve") est interposée sur la conduite 16 en amont du moteur 20.Reference numeral 10 denotes an aircraft fuel tank with a fuel pump 12 driven by an electric motor 14 and supplying a line 16 which conveys fuel to the engine 20. A low-pressure shut-off valve 18 or LPSOV ("Low Pressure Shutoff"). Off Valve ") is interposed on the pipe 16 upstream of the engine 20.

Le moteur 20 comprend un dispositif de pompage 22 fournissant du carburant à un circuit principal d'alimentation de la chambre de combustion du moteur en carburant haute pression.The engine 20 includes a pumping device 22 supplying fuel to a main fuel supply circuit of the engine combustion chamber with high pressure fuel.

A cet effet, le dispositif de pompage 22 comprend une pompe de carburant basse pression 24 dont l'entrée est reliée à la conduite 16 et dont la sortie est reliée à l'entrée d'une pompe de carburant haute pression 26 par une conduite 28. La sortie de la pompe haute pression 26 est reliée à une conduite 30 du circuit principal d'alimentation. Un dispositif de dosage 32 reçoit le débit de carburant fourni par la pompe haute pression afin d'alimenter la chambre de combustion (non représentée) du moteur par un débit régulé de carburant haute pression.For this purpose, the pumping device 22 comprises a low-pressure fuel pump 24 whose inlet is connected to the pipe 16 and whose outlet is connected to the inlet of a high-pressure fuel pump 26 via a pipe 28. The output of the high pressure pump 26 is connected to a line 30 of the main supply circuit. A metering device 32 receives the fuel flow supplied by the high pressure pump to supply the combustion chamber (not shown) of the engine with a regulated high pressure fuel flow rate.

La pompe basse pression 24 est par exemple une pompe centrifuge entraînée mécaniquement par l'intermédiaire de l'AGB. La pompe haute pression 26 est ici une pompe à engrenages également entraînée mécaniquement par l'intermédiaire de l'AGB.The low pressure pump 24 is for example a centrifugal pump driven mechanically via the AGB. The high pressure pump 26 is here a gear pump also driven mechanically via the AGB.

Le moteur 20 comprend un dispositif électrique de démarrage 40, par exemple de type S/G. Le dispositif 40 est logé dans un carter 42. Il comporte une machine électrique 44 ayant un arbre 46 qui fait saillie hors du carter 42 pour couplage mécanique avec l'AGB. En régime de démarrage, la machine électrique fonctionne en mode moteur pour entraîner un arbre de turbine par l'intermédiaire de l'AGB tandis qu'après démarrage, lorsque l'arbre de turbine a atteint une vitesse suffisante, le fonctionnement de la machine électrique est commuté en mode génératrice. Un boîtier 48 renferme l'électronique de puissance pour la commande de la machine électrique 44. Le boîtier est relié électriquement à un circuit de régulation électronique du moteur (non représenté). Le boîtier 48 peut être fixé au carter 42 comme illustré, ou être indépendant de celui-ci.The motor 20 comprises an electric starting device 40, for example of the S / G type. The device 40 is housed in a housing 42. It comprises an electric machine 44 having a shaft 46 which protrudes out of the housing 42 for mechanical coupling with the AGB. In start-up mode, the electric machine operates in motor mode to drive a turbine shaft through the AGB while after starting, when the turbine shaft has reached a sufficient speed, the operation of the electric machine is switched to generator mode. A housing 48 encloses the power electronics for the control of the electrical machine 44. The housing is electrically connected to an electronic engine control circuit (not shown). The housing 48 may be attached to the housing 42 as illustrated, or be independent therefrom.

Conformément à l'invention, le refroidissement du dispositif électrique de démarrage 40 est assuré par du carburant prélevé dans le dispositif de pompage par une pompe 50 entraînée par un moteur électrique 52 lui-même commandé par le circuit de régulation électronique du moteur, l'entraînement de la pompe 50 étant ainsi indépendant de celui de la pompe haute pression 26.According to the invention, the cooling of the electric starting device 40 is provided by fuel taken from the pumping device by a pump 50 driven by an electric motor 52 itself controlled by the electronic engine control circuit, the driving the pump 50 thus being independent of that of the high pressure pump 26.

Dans l'exemple illustré, le refroidissement est assuré par échange thermique avec un fluide caloporteur prélevant des calories dans le dispositif de démarrage 40.In the example illustrated, the cooling is ensured by heat exchange with a coolant collecting calories in the starting device 40.

Des canaux de circulation de fluide caloporteur 42a sont formés dans les parois du carter 42 et à proximité du boîtier 48. Le fluide caloporteur est par exemple de l'huile utilisée également pour lubrification de divers organes dont l'AGB. Le circuit d'huile avec pompe à huile (non représentée) comprend une conduite 54 qui amène l'huile aux canaux 42a et une conduite 56 qui récupère l'huile ayant circulé dans les canaux 42a et, le cas échéant, ayant aussi été utilisée pour lubrification de paliers supportant l'arbre 46 dans le boîtier 42.Heat transfer fluid circulation channels 42a are formed in the walls of the casing 42 and close to the casing 48. The fluid coolant is for example oil also used for lubrication of various organs including AGB. The oil circuit with an oil pump (not shown) comprises a conduit 54 which leads the oil to the channels 42a and a conduit 56 which recovers the oil having circulated in the channels 42 a and, where appropriate, also having used for bearing lubrication bearing shaft 46 in housing 42.

L'échange thermique entre le carburant et l'huile est réalisé au sein d'un échangeur 58. L'échangeur 58 comprend un circuit interne d'huile qui reçoit l'huile provenant du dispositif de démarrage 40 par la conduite 56 et qui restitue l'huile refroidie au circuit d'huile, et un circuit interne de carburant faisant partie d'un circuit de carburant 60 qui a une entrée reliée à la sortie de la pompe 50 et une sortie reliée au réservoir 10.The heat exchange between the fuel and the oil is carried out within an exchanger 58. The exchanger 58 comprises an internal oil circuit which receives the oil from the starting device 40 via the pipe 56 and which restores the oil cooled to the oil circuit, and an internal fuel circuit forming part of a fuel circuit 60 which has an input connected to the output of the pump 50 and an output connected to the tank 10.

Dans l'exemple illustré, l'entrée de la pompe 50 est reliée à la conduite 28, c'est-à-dire entre la sortie de la pompe basse pression 24 et l'entrée de la pompe haute pression 26. Ainsi, après démarrage, la pompe électrique 50 peut être arrêtée, la vitesse de l'arbre de turbine entraînant la pompe basse pression 24 devenant suffisante pour fournir le débit de carburant de refroidissement requis pour refroidir efficacement le dispositif de démarrage après commutation de la machine 44 en mode génératrice. L'arrêt de la pompe 50 est commandé par désactivation du moteur électrique 52 sous la commande de l'unité de régulation électronique du moteur lorsque la vitesse de l'arbre de turbine dépasse une valeur minimale donnée.In the illustrated example, the inlet of the pump 50 is connected to the pipe 28, that is to say between the output of the low pressure pump 24 and the inlet of the high pressure pump 26. Thus, after starting, the electric pump 50 can be stopped, the speed of the turbine shaft driving the low pressure pump 24 becoming sufficient to provide the cooling fuel flow rate required to effectively cool the starting device after switching the machine 44 into operation. generator. The stopping of the pump 50 is controlled by deactivation of the electric motor 52 under the control of the electronic engine control unit when the speed of the turbine shaft exceeds a given minimum value.

Dans le cas où le dispositif de pompage comprend seulement une pompe haute pression alimentée directement par la pompe de carburant du réservoir 10, la pompe électrique 50 est reliée à la conduite alimentant la pompe haute pression.In the case where the pumping device comprises only a high pressure pump supplied directly by the fuel pump of the tank 10, the electric pump 50 is connected to the pipe supplying the high pressure pump.

Comme montré sur la figure 2, la sortie de la pompe électrique 50 peut être reliée également par une conduite 62 à la conduite 30 du circuit principal d'alimentation en carburant sous pression, en amont du dispositif de dosage 32. Ainsi, pendant la phase de démarrage, la pompe 50 peut contribuer à la fourniture d'un débit suffisant de carburant à la chambre de combustion. Cette exigence de fourniture de débit de carburant suffisant pendant le démarrage ne pesant plus sur la pompe haute pression 26, on pourra alors avantageusement utiliser pour celle-ci une pompe centrifuge plutôt qu'une pompe volumétrique à engrenages. Un clapet anti-retour 64 est monté sur la conduite 62 pour éviter qu'après démarrage, du carburant issu de la pompe haute pression 26 circule dans la conduite 62.As shown on the figure 2 , the output of the electric pump 50 can also be connected via a line 62 to the pipe 30 of the main circuit for supplying pressurized fuel, upstream of the metering device 32. Thus, during the starting phase, the pump 50 can contribute to the provision of sufficient fuel flow to the combustion chamber. This requirement to provide sufficient fuel flow during startup no longer weighs on the high pressure pump 26, we can then advantageously use for it a centrifugal pump rather than a positive displacement gear pump. A nonreturn valve 64 is mounted on the pipe 62 to prevent, after starting, fuel from the high pressure pump 26 circulating in the pipe 62.

Dans ce qui précède, il a été envisagé un refroidissement du dispositif de démarrage par le carburant de façon indirecte, par l'intermédiaire d'huile agissant comme fluide caloporteur. On pourra bien entendu utiliser un autre fluide caloporteur, voire réaliser directement le refroidissement du dispositif de démarrage par le carburant en faisant circuler le carburant dans le dispositif de démarrage.In the foregoing, it has been envisaged a cooling of the starting device by the fuel indirectly, through oil acting as heat transfer fluid. It will of course be possible to use another heat transfer fluid, or even carry out the cooling of the starting device directly by the fuel by circulating the fuel in the starting device.

Claims (6)

  1. An aeronautical engine comprising a fuel pumping device including a high pressure pump (26) having an inlet connected to a low pressure fuel conduit (28) and an outlet connected to a main circuit for feeding high pressure fuel, an electric device (40) for starting the engine and a cooling device of the electric starting device connected to the pumping device in order to ensure cooling by circulation of fuel,
    characterized in that the cooling device (54, 56, 58) is supplied with fuel through a pump (50) driven by an electric motor (52) independently of the high pressure pump (26) and having an inlet connected to the pumping device, upstream from the high pressure pump (26).
  2. An aeronautical engine according to claim 1, wherein the pumping device comprises a low pressure pump (24) driven from a shaft of the engine and having an outlet connected to the inlet of the high pressure pump (26),
    characterized in that the electric pump (50) feeding the cooling device has its inlet connected to the pumping device between the outlet of the low pressure pump (24) and the inlet of the high pressure pump (26).
  3. An aeronautical engine according to any of claims 1 and 2, characterized in that the electric pump (50) feeding the cooling device has an outlet connected to the main circuit (30) for feeding high pressure fuel.
  4. An aeronautical engine according to claim 3, characterized in that the high pressure pump (26) is a centrifugal pump.
  5. An aeronautical engine according to any of claims 1 to 3, characterized in that the cooling device comprises a first circuit (54, 56) for circulating a heat transfer fluid, connected to the electric starting device, a second circuit (60) for circulating fuel connected to the electric pump (50) feeding the cooling device and a heat exchanger (58) passed through by the first and the second circuit.
  6. An aeronautical engine according to any of claims 1 to 4, characterized in that the cooling device is designed so as to cool an electric starter of the electric starting device (40) and an electronic circuit (48) for controlling the power of the electric starter.
EP10706305A 2009-02-16 2010-01-15 Aircraft engine with cooling for an electric starting device Active EP2396526B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0950976A FR2942271B1 (en) 2009-02-16 2009-02-16 AERONAUTICAL MOTOR WITH COOLING OF AN ELECTRIC START-UP DEVICE
PCT/FR2010/050060 WO2010092267A1 (en) 2009-02-16 2010-01-15 Aircraft engine with cooling for an electric starting device

Publications (2)

Publication Number Publication Date
EP2396526A1 EP2396526A1 (en) 2011-12-21
EP2396526B1 true EP2396526B1 (en) 2013-01-02

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US (1) US9394832B2 (en)
EP (1) EP2396526B1 (en)
JP (1) JP5384670B2 (en)
CN (1) CN102317599B (en)
BR (1) BRPI1008872B1 (en)
CA (1) CA2752526C (en)
FR (1) FR2942271B1 (en)
RU (1) RU2515912C2 (en)
WO (1) WO2010092267A1 (en)

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FR3021359B1 (en) * 2014-05-26 2019-06-07 Safran Power Units DEVICE AND METHOD FOR PREHEATING FUEL IN A TURBOMACHINE
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Publication number Publication date
CA2752526A1 (en) 2010-08-19
BRPI1008872A2 (en) 2017-05-16
BRPI1008872B1 (en) 2020-11-17
EP2396526A1 (en) 2011-12-21
FR2942271A1 (en) 2010-08-20
JP5384670B2 (en) 2014-01-08
CN102317599B (en) 2013-10-09
RU2011138010A (en) 2013-03-27
JP2012518151A (en) 2012-08-09
WO2010092267A1 (en) 2010-08-19
CN102317599A (en) 2012-01-11
US9394832B2 (en) 2016-07-19
FR2942271B1 (en) 2011-05-13
RU2515912C2 (en) 2014-05-20
US20110296846A1 (en) 2011-12-08
CA2752526C (en) 2017-05-16

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